Airworthiness Directives; The Boeing Company Airplanes, 62031-62035 [2016-21147]

Download as PDF Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Proposed Rules Airworthiness Limitations Section inspection is insufficient to detect early crack development. We are issuing this AD to detect and correct cracks in the fuselage skin; such cracking could result in reduced structural integrity of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection Within the compliance time specified in paragraphs (g)(1) and (g)(2) of this AD, as applicable, do high and low frequency eddy current inspections for cracks in the fuselage skin around the largest traffic collision avoidance system (TCAS) antenna external doubler and of the longitudinal lap joint at fuselage stringer STR37 between fuselage station (STA) STA6805 and STA7305, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–53–130, dated December 01, 2015. (1) For airplanes having 45,000 or more flight cycles as of the effective date of this AD, since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness: Do the high and low frequency eddy current inspections within 750 flight cycles after the effective date of this AD. (2) For airplanes having 40,000 or more flight cycles, but less than 45,000 flight cycles as of the effective date of this AD, since the date of issuance of the original airworthiness certificate or the date of issuance of the original export certificate of airworthiness: Do the high and low frequency eddy current inspections within 1,500 flight cycles after the effective date of this AD. mstockstill on DSK3G9T082PROD with PROPOSALS (h) Corrective Action If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Fokker B.V. Service’s EASA Design Organization Approval (DOA). (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal VerDate Sep<11>2014 16:36 Sep 07, 2016 Jkt 238001 inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Fokker Services B.V.’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0029, dated February 23, 2016, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–9058. (2) For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone: +31 (0)88–6280–350; fax: +31 (0)88–6280–111; email: technicalservices@ fokker.com; Internet https://www.myfokker fleet.com. You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on August 24, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–21151 Filed 9–7–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9067; Directorate Identifier 2016–NM–043–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 747–100, 747– 100B, 747–100B SUD, 747–200B, 747– 200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. This proposed AD was prompted by a report of incidents involving fatigue cracking in transport category airplanes that are approaching SUMMARY: PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 62031 or have exceeded their design service objective and a structural reevaluation by the manufacturer that identified additional structural elements that qualify as structural significant items (SSIs). This proposed AD would require revising the maintenance or inspection program, as applicable, to include inspections that will give no less than the required damage tolerance rating (DTR) for certain SSIs, and repairing any cracked structure. This proposed AD would also require inspections to detect cracks of all SSI structure, and repair if necessary. We are proposing this AD to ensure the continued structural integrity of all The Boeing Company Model 747– 100, 747–100B, 747–100B SUD, 747– 200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. DATES: We must receive comments on this proposed AD by October 24, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206– 766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9067; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office E:\FR\FM\08SEP1.SGM 08SEP1 62032 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Proposed Rules (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: nathan.p.weigand@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2016–9067; Directorate Identifier 2016– NM–043–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On December 26, 2007, we issued AD 2004–07–22 R1, Amendment 39–15326 (73 FR 1052, January 7, 2008); corrected February 14, 2008 (73 FR 8589) (‘‘AD 2004–07–22 R1’’); for all The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747– 400D, 747–400F, 747SR, and 747SP series airplanes. AD 2004–07–22 R1 requires that the maintenance inspection program be revised to include inspections that will give no less than the required DTR for each SSI, and repair of cracked structure. AD 2004–07–22 R1 was prompted by a report of incidents involving fatigue cracking in transport category airplanes that are approaching or have exceeded their design service objective. We issued AD 2004–07–22 R1 to ensure the continued structural integrity of all Boeing Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747– 200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. Actions Since AD 2004–07–22 R1 Was Issued Since we issued AD 2004–07–22 R1, a structural reevaluation by the manufacturer identified additional structural elements that qualify as SSIs. We have determined that supplemental inspections are required for timely detection of fatigue cracking for these additional structural elements. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013. The service information describes procedures for inspections to detect cracks of all structure identified as SSIs and includes six new SSIs since the last revision. We also reviewed Boeing Document No. D6–35022–1, ‘‘747–400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015. The service information describes procedures for inspections of wing, fuselage, and empennage SSIs for Model 747–400 LCF airplanes. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require revising the maintenance or inspection program, as applicable, to include inspections that will give no less than the required DTR for certain SSIs, and repairing any cracked structure. This proposed AD would also require inspections to detect cracks of all SSI structure, and repair if necessary. This proposed AD does not supersede 2004–07–22 R1. However, accomplishing the revision specified in paragraph (h) of this proposed AD would terminate the requirements of paragraphs (f), (g), and (h) of AD 2004– 07–22 R1. Also, doing an inspection specified in paragraph (i) of this proposed AD would terminate the corresponding inspection required by paragraph (i) of AD 2004–07–22 R1. Costs of Compliance We estimate that this proposed AD affects 118 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Cost on U.S. operators Revision of maintenance or inspection program. mstockstill on DSK3G9T082PROD with PROPOSALS Action 1 work-hour × $85 per hour = $85 ................. $0 $85 $10,030 We have not specified cost estimates for the inspection and repair specified in this proposed AD. Compliance with this proposed AD constitutes a method of compliance with the FAA aging airplane safety final rule (AASFR) (70 FR 5518, February 2, 2005) for certain baseline structure of Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes. The AASFR VerDate Sep<11>2014 16:36 Sep 07, 2016 Jkt 238001 requires certain operators to incorporate damage tolerance inspections into their maintenance inspection programs. These requirements are described in 14 CFR 121.1109(c)(1) and 14 CFR 129.109(b)(1). Accomplishment of the actions specified in this proposed AD will meet the requirements of these regulations for certain baseline structure. The costs for accomplishing the inspection portion of this proposed PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 AD were accounted for in the regulatory evaluation of the AASFR. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. E:\FR\FM\08SEP1.SGM 08SEP1 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Proposed Rules We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: mstockstill on DSK3G9T082PROD with PROPOSALS ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2016–9067; Directorate Identifier 2016– NM–043–AD. VerDate Sep<11>2014 16:36 Sep 07, 2016 Jkt 238001 (a) Comments Due Date We must receive comments by October 24, 2016. (b) Affected ADs This AD affects AD 2004–07–22 R1, Amendment 39–15326 (73 FR 1052, January 7, 2008); corrected February 14, 2008 (73 FR 8589) (‘‘AD 2004–07–22 R1’’). (c) Applicability This AD applies to all The Boeing Company Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category. Note 1 to paragraph (c) of this AD: A Model 747–400 LCF airplane is a Model 747– 400 series airplane that has been modified from a passenger airplane to a freighter configuration as specified in Boeing Service Bulletin 747–00–2084. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage; 54, Nacelles/ Pylons; 55, Stabilizers; 57, Wings. (e) Unsafe Condition This AD was prompted by a report of incidents involving fatigue cracking in transport category airplanes that are approaching or have exceeded their design service objective and a structural reevaluation by the manufacturer that identified additional structural elements that qualify as structural significant items (SSIs). We are issuing this AD to ensure the continued structural integrity of all The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747– 200F, 747–300, 747–400, 747–400D, 747– 400F, 747SR, and 747SP series airplanes. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of SSI For the purposes of this AD, an SSI is defined as a principal structural element (PSE). A PSE is a structural element that contributes significantly to the carrying of flight, ground, or pressurization loads, and whose integrity is essential in maintaining the overall structural integrity of the airplane. (h) Maintenance or Inspection Program Revision for All Airplanes Prior to reaching the compliance thresholds specified in paragraph (i)(1)(i), (i)(2)(i), (j)(1)(i), or (j)(2)(i) of this AD, as applicable, or within 12 months after the effective date of this AD, whichever occurs later: Incorporate a revision into the maintenance or inspection program, as applicable, that provides no less than the required damage tolerance rating (DTR) for each SSI listed in the applicable service information specified in paragraph (h)(1) or (h)(2) of this AD. The revision to the maintenance or inspection program must include, and must be implemented in accordance with, the procedures in Section PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 62033 5.0, ‘‘Damage Tolerance Rating (DTR) System Application,’’ of Boeing Document No. D6– 35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013; and Boeing Document No. D6–35022–1, ‘‘747– 400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015; as applicable. Accomplishing the revision required by this paragraph terminates the actions required by paragraphs (f), (g), and (h) of AD 2004–07–22 R1. After accomplishing the revision required by this paragraph, the revisions required by paragraphs (f), (g), and (h) of AD 2004–07– 22 R1, as applicable, must be removed. (1) For all airplanes except Model 747–400 LCF airplanes: SSIs listed in Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013. (2) For Model 747–400 LCF airplanes: SSIs listed in Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013; and SSIs listed in Boeing Document No. D6–35022–1, ‘‘747–400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015. For SSIs listed in both Boeing Document No. D6–35022–1, ‘‘747– 400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015; and Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013: Incorporate the SSIs listed Boeing Document No. D6–35022–1, ‘‘747–400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015. (i) Inspection Compliance Times for All Model 747 Airplanes Except Model 747–400 LCF airplanes For all Model 747 airplanes except Model 747–400 LCF airplanes: Perform inspections to detect cracks of all structure identified in Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013, at the times specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD, as applicable. Once the initial inspection has been performed, in order to remain in compliance with the maintenance or inspection program, as required by paragraph (h) of this AD, repetitive inspections are required at the intervals specified in Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013. Doing an inspection required by this paragraph terminates the corresponding inspection required by paragraph (i) of AD 2004–07–22 R1. (1) For wing structure, except as provided by paragraph (i)(3) of this AD: Inspect at the times specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, whichever occurs later. (i) Within the applicable compliance time specified in paragraph (i)(1)(i)(A) or (i)(1)(i)(B) of this AD. E:\FR\FM\08SEP1.SGM 08SEP1 62034 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Proposed Rules mstockstill on DSK3G9T082PROD with PROPOSALS (A) For all Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747SR, and 747SP series airplanes: Prior to the accumulation of 20,000 total flight cycles or 100,000 total flight hours, whichever occurs first. (B) For all Model 747–400, 747–400D, and 747–400F series airplanes: Prior to the accumulation of 20,000 total flight cycles or 115,000 total flight hours, whichever occurs first. (ii) Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs later. (2) For all structure other than wing structure, except as provided by paragraph (i)(3) of this AD: At the time specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD, whichever occurs later. (i) Prior to the accumulation of 20,000 total flight cycles. (ii) Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs later. (3) For any portion of an SSI that has been replaced with new structure: Inspect at the later of the times specified in paragraphs (i)(3)(i) and (i)(3)(ii) of this AD. (i) At the time specified in paragraph (i)(1) or (i)(2) of this AD, as applicable. (ii) Within 10,000 flight cycles after the replacement of the part with a new part. (j) Inspection Compliance Times for Model 747–400 LCF Airplanes For Model 747–400 LCF airplanes: Perform inspections to detect cracks of all structure identified in Boeing Document No. D6– 35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013; and Boeing Document No. D6–35022–1, ‘‘747– 400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015; at the times specified in paragraph (j)(1) or (j)(2) of this AD, as applicable. Once the initial inspection has been performed, in order to remain in compliance with the maintenance or inspection program, as required by paragraph (h) of this AD, repetitive inspections are required at the intervals specified in Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013; and Boeing Document No. D6–35022– 1, ‘‘747–400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015. Where SSIs are listed in both Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013; and Boeing Document No. D6–35022–1, ‘‘747– 400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015; the SSIs listed in Boeing Document No. D6–35022–1, ‘‘747–400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015, take precedence. Doing an inspection required by this paragraph terminates the corresponding inspection required by paragraph (i) of AD 2004–07–22 R1. (1) For wing structure: Inspect at the times specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD, whichever occurs later. VerDate Sep<11>2014 16:36 Sep 07, 2016 Jkt 238001 (i) Prior to the accumulation of 20,000 total flight cycles or 115,000 total flight hours, whichever occurs first. (ii) Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs later. (2) For all structure other than wing structure: At the time specified in paragraph (j)(2)(i) or (i)(2)(ii) of this AD, whichever occurs later. (i) At the earlier of the times specified in paragraphs (j)(2)(i)(A) and (j)(2)(i)(B) of this AD. (A) Prior to the accumulation of 20,000 total flight cycles. (B) Within the applicable initial compliance time specified in Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013; and Boeing Document No. D6–35022– 1, ‘‘747–400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015. Where SSIs are listed in both Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013; and Boeing Document No. D6–35022–1, ‘‘747– 400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015; the SSIs listed in Boeing Document No. D6–35022–1, ‘‘747–400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015, take precedence. (ii) Within 1,000 flight cycles or 12 months after the effective date of this AD, whichever occurs later. (k) Repair If any cracked structure is found during any inspection required by paragraph (i) or (j) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (l) Inspection Program for Transferred Airplanes Before any airplane that is subject to this AD and that has exceeded the applicable compliance times specified in paragraph (i) or (j) of this AD can be added to an air carrier’s operations specifications, a program for the accomplishment of the inspections required by this AD must be established in accordance with paragraph (l)(1) or (l)(2) of this AD, as applicable. (1) For airplanes that have been inspected as specified in this AD, the inspection of each SSI must be accomplished by the new operator using the previous operator’s schedule and inspection method, or the new operator’s schedule and inspection method, at whichever time would result in the earlier accomplishment for that SSI inspection. The compliance time for accomplishment of this inspection must be measured from the last inspection accomplished by the previous operator. After each inspection has been performed once, each subsequent inspection must be performed using the new operator’s schedule and inspection method. (2) For airplanes that have not been inspected as specified in this AD, the inspection of each SSI required by this AD PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 must be accomplished either prior to adding the airplane to the air carrier’s operations specification, or using a schedule and an inspection method approved by the Manager, Seattle Aircraft Certification Office (ACO). After each inspection has been performed once, each subsequent inspection must be performed using the new operator’s schedule and inspection method. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (n)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved for AD 2004–07–22 R1 are approved as AMOCs for the corresponding provisions of paragraphs (h), (i), and (j) of this AD for the SSIs identified in the AMOC, except for any SSI that has an expanded inspection area identified in Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document for Model 747 Airplanes,’’ Revision H, dated September 2013; or Boeing Document No. D6–35022–1, ‘‘747–400 LCF Supplemental Structural Inspection Document—Appendix A,’’ dated November 2015. (n) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917– 6428; fax: 425–917–6590; email: nathan.p.weigand@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. E:\FR\FM\08SEP1.SGM 08SEP1 Federal Register / Vol. 81, No. 174 / Thursday, September 8, 2016 / Proposed Rules Issued in Renton, Washington, on August 24, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–21147 Filed 9–7–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9071; Directorate Identifier 2016–NM–019–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) which indicates that the main landing gear (MLG) does not comply with certification specifications, which could result in a locking failure of the MLG side stay. This proposed AD would require modification or replacement of certain MLG side stay assemblies. We are proposing this AD to prevent possible collapse of the MLG during takeoff and landing. DATES: We must receive comments on this proposed AD by October 24, 2016. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: mstockstill on DSK3G9T082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:36 Sep 07, 2016 Jkt 238001 account.airworth-eas@airbus.com; Internet: https://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425 227–1221. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9071; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1405; fax: 425–227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–9071; Directorate Identifier 2016–NM–019–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0018, dated January 19, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A318, A319, PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 62035 A320, and A321 series airplanes. The MCAI states: During studies for a new landing gear design, it was discovered that the singlelocked upper and lower cardan joints of the MLG do not comply with the certification specifications of (CS), (formerly Joint Aviation Requirements (JAR)) Part 25.607. This condition, if not corrected, could lead to MLG side stay locking failure that, during take-off and landing, may result in damage to the aeroplane and detrimental effect on safe flight. To address this potential unsafe condition, the MLG manufacturer developed a modification to change the single-locked MLG joint into a double-locked one. This modification is available for in-service application through Messier-Bugatti-Dowty (MBD) Service Bulletin (SB) 200–32–315 or SB 201–32–63, or Airbus SB A320–32–1429. For the reasons described above, this [EASA] AD requires modification or replacement of the MLG side stay assemblies to introduce the double locking of the MLG upper and lower cardan joints. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9071. Related Service Information Under 1 CFR Part 51 We have reviewed the following service information. The service information describes procedures for modifying the MLG side stay assembly. • Airbus Service Bulletin A320–32– 1429, dated September 10, 2015. • Messier-Bugatti-Dowty Service Bulletin 200–32–315, dated April 24, 2015. • Messier-Bugatti-Dowty Service Bulletin 201–32–63, dated April 24, 2015. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. E:\FR\FM\08SEP1.SGM 08SEP1

Agencies

[Federal Register Volume 81, Number 174 (Thursday, September 8, 2016)]
[Proposed Rules]
[Pages 62031-62035]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-21147]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9067; Directorate Identifier 2016-NM-043-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 
747SP series airplanes. This proposed AD was prompted by a report of 
incidents involving fatigue cracking in transport category airplanes 
that are approaching or have exceeded their design service objective 
and a structural reevaluation by the manufacturer that identified 
additional structural elements that qualify as structural significant 
items (SSIs). This proposed AD would require revising the maintenance 
or inspection program, as applicable, to include inspections that will 
give no less than the required damage tolerance rating (DTR) for 
certain SSIs, and repairing any cracked structure. This proposed AD 
would also require inspections to detect cracks of all SSI structure, 
and repair if necessary. We are proposing this AD to ensure the 
continued structural integrity of all The Boeing Company Model 747-100, 
747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 
747-400D, 747-400F, 747SR, and 747SP series airplanes.

DATES: We must receive comments on this proposed AD by October 24, 
2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, 
extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9067; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office

[[Page 62032]]

(phone: 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: nathan.p.weigand@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2016-9067; 
Directorate Identifier 2016-NM-043-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On December 26, 2007, we issued AD 2004-07-22 R1, Amendment 39-
15326 (73 FR 1052, January 7, 2008); corrected February 14, 2008 (73 FR 
8589) (``AD 2004-07-22 R1''); for all The Boeing Company Model 747-100, 
747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 
747-400D, 747-400F, 747SR, and 747SP series airplanes. AD 2004-07-22 R1 
requires that the maintenance inspection program be revised to include 
inspections that will give no less than the required DTR for each SSI, 
and repair of cracked structure. AD 2004-07-22 R1 was prompted by a 
report of incidents involving fatigue cracking in transport category 
airplanes that are approaching or have exceeded their design service 
objective. We issued AD 2004-07-22 R1 to ensure the continued 
structural integrity of all Boeing Model 747-100, 747-100B, 747-100B 
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-
400F, 747SR, and 747SP series airplanes.

Actions Since AD 2004-07-22 R1 Was Issued

    Since we issued AD 2004-07-22 R1, a structural reevaluation by the 
manufacturer identified additional structural elements that qualify as 
SSIs. We have determined that supplemental inspections are required for 
timely detection of fatigue cracking for these additional structural 
elements.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Document No. D6-35022, ``Supplemental Structural 
Inspection Document for Model 747 Airplanes,'' Revision H, dated 
September 2013. The service information describes procedures for 
inspections to detect cracks of all structure identified as SSIs and 
includes six new SSIs since the last revision.
    We also reviewed Boeing Document No. D6-35022-1, ``747-400 LCF 
Supplemental Structural Inspection Document--Appendix A,'' dated 
November 2015. The service information describes procedures for 
inspections of wing, fuselage, and empennage SSIs for Model 747-400 LCF 
airplanes.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require revising the maintenance or 
inspection program, as applicable, to include inspections that will 
give no less than the required DTR for certain SSIs, and repairing any 
cracked structure. This proposed AD would also require inspections to 
detect cracks of all SSI structure, and repair if necessary.
    This proposed AD does not supersede 2004-07-22 R1. However, 
accomplishing the revision specified in paragraph (h) of this proposed 
AD would terminate the requirements of paragraphs (f), (g), and (h) of 
AD 2004-07-22 R1. Also, doing an inspection specified in paragraph (i) 
of this proposed AD would terminate the corresponding inspection 
required by paragraph (i) of AD 2004-07-22 R1.

Costs of Compliance

    We estimate that this proposed AD affects 118 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per      Cost on  U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Revision of maintenance or            1 work-hour x $85 per                $0              $85          $10,030
 inspection program.                   hour = $85.
----------------------------------------------------------------------------------------------------------------

    We have not specified cost estimates for the inspection and repair 
specified in this proposed AD. Compliance with this proposed AD 
constitutes a method of compliance with the FAA aging airplane safety 
final rule (AASFR) (70 FR 5518, February 2, 2005) for certain baseline 
structure of Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 
747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series 
airplanes. The AASFR requires certain operators to incorporate damage 
tolerance inspections into their maintenance inspection programs. These 
requirements are described in 14 CFR 121.1109(c)(1) and 14 CFR 
129.109(b)(1). Accomplishment of the actions specified in this proposed 
AD will meet the requirements of these regulations for certain baseline 
structure. The costs for accomplishing the inspection portion of this 
proposed AD were accounted for in the regulatory evaluation of the 
AASFR.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.

[[Page 62033]]

    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2016-9067; Directorate Identifier 
2016-NM-043-AD.

(a) Comments Due Date

    We must receive comments by October 24, 2016.

(b) Affected ADs

    This AD affects AD 2004-07-22 R1, Amendment 39-15326 (73 FR 
1052, January 7, 2008); corrected February 14, 2008 (73 FR 8589) 
(``AD 2004-07-22 R1'').

(c) Applicability

    This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 
747-400D, 747-400F, 747SR, and 747SP series airplanes, certificated 
in any category.

    Note 1 to paragraph (c) of this AD: A Model 747-400 LCF airplane 
is a Model 747-400 series airplane that has been modified from a 
passenger airplane to a freighter configuration as specified in 
Boeing Service Bulletin 747-00-2084.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage; 
54, Nacelles/Pylons; 55, Stabilizers; 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report of incidents involving fatigue 
cracking in transport category airplanes that are approaching or 
have exceeded their design service objective and a structural 
reevaluation by the manufacturer that identified additional 
structural elements that qualify as structural significant items 
(SSIs). We are issuing this AD to ensure the continued structural 
integrity of all The Boeing Company Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, 747SR, and 747SP series airplanes.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Definition of SSI

    For the purposes of this AD, an SSI is defined as a principal 
structural element (PSE). A PSE is a structural element that 
contributes significantly to the carrying of flight, ground, or 
pressurization loads, and whose integrity is essential in 
maintaining the overall structural integrity of the airplane.

(h) Maintenance or Inspection Program Revision for All Airplanes

    Prior to reaching the compliance thresholds specified in 
paragraph (i)(1)(i), (i)(2)(i), (j)(1)(i), or (j)(2)(i) of this AD, 
as applicable, or within 12 months after the effective date of this 
AD, whichever occurs later: Incorporate a revision into the 
maintenance or inspection program, as applicable, that provides no 
less than the required damage tolerance rating (DTR) for each SSI 
listed in the applicable service information specified in paragraph 
(h)(1) or (h)(2) of this AD. The revision to the maintenance or 
inspection program must include, and must be implemented in 
accordance with, the procedures in Section 5.0, ``Damage Tolerance 
Rating (DTR) System Application,'' of Boeing Document No. D6-35022, 
``Supplemental Structural Inspection Document for Model 747 
Airplanes,'' Revision H, dated September 2013; and Boeing Document 
No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection 
Document--Appendix A,'' dated November 2015; as applicable. 
Accomplishing the revision required by this paragraph terminates the 
actions required by paragraphs (f), (g), and (h) of AD 2004-07-22 
R1. After accomplishing the revision required by this paragraph, the 
revisions required by paragraphs (f), (g), and (h) of AD 2004-07-22 
R1, as applicable, must be removed.
    (1) For all airplanes except Model 747-400 LCF airplanes: SSIs 
listed in Boeing Document No. D6-35022, ``Supplemental Structural 
Inspection Document for Model 747 Airplanes,'' Revision H, dated 
September 2013.
    (2) For Model 747-400 LCF airplanes: SSIs listed in Boeing 
Document No. D6-35022, ``Supplemental Structural Inspection Document 
for Model 747 Airplanes,'' Revision H, dated September 2013; and 
SSIs listed in Boeing Document No. D6-35022-1, ``747-400 LCF 
Supplemental Structural Inspection Document--Appendix A,'' dated 
November 2015. For SSIs listed in both Boeing Document No. D6-35022-
1, ``747-400 LCF Supplemental Structural Inspection Document--
Appendix A,'' dated November 2015; and Boeing Document No. D6-35022, 
``Supplemental Structural Inspection Document for Model 747 
Airplanes,'' Revision H, dated September 2013: Incorporate the SSIs 
listed Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental 
Structural Inspection Document--Appendix A,'' dated November 2015.

(i) Inspection Compliance Times for All Model 747 Airplanes Except 
Model 747-400 LCF airplanes

    For all Model 747 airplanes except Model 747-400 LCF airplanes: 
Perform inspections to detect cracks of all structure identified in 
Boeing Document No. D6-35022, ``Supplemental Structural Inspection 
Document for Model 747 Airplanes,'' Revision H, dated September 
2013, at the times specified in paragraph (i)(1), (i)(2), or (i)(3) 
of this AD, as applicable. Once the initial inspection has been 
performed, in order to remain in compliance with the maintenance or 
inspection program, as required by paragraph (h) of this AD, 
repetitive inspections are required at the intervals specified in 
Boeing Document No. D6-35022, ``Supplemental Structural Inspection 
Document for Model 747 Airplanes,'' Revision H, dated September 
2013. Doing an inspection required by this paragraph terminates the 
corresponding inspection required by paragraph (i) of AD 2004-07-22 
R1.
    (1) For wing structure, except as provided by paragraph (i)(3) 
of this AD: Inspect at the times specified in paragraph (i)(1)(i) or 
(i)(1)(ii) of this AD, whichever occurs later.
    (i) Within the applicable compliance time specified in paragraph 
(i)(1)(i)(A) or (i)(1)(i)(B) of this AD.

[[Page 62034]]

    (A) For all Model 747-100, 747-100B, 747-100B SUD, 747-200B, 
747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes: 
Prior to the accumulation of 20,000 total flight cycles or 100,000 
total flight hours, whichever occurs first.
    (B) For all Model 747-400, 747-400D, and 747-400F series 
airplanes: Prior to the accumulation of 20,000 total flight cycles 
or 115,000 total flight hours, whichever occurs first.
    (ii) Within 1,000 flight cycles or 12 months after the effective 
date of this AD, whichever occurs later.
    (2) For all structure other than wing structure, except as 
provided by paragraph (i)(3) of this AD: At the time specified in 
paragraph (i)(2)(i) or (i)(2)(ii) of this AD, whichever occurs 
later.
    (i) Prior to the accumulation of 20,000 total flight cycles.
    (ii) Within 1,000 flight cycles or 12 months after the effective 
date of this AD, whichever occurs later.
    (3) For any portion of an SSI that has been replaced with new 
structure: Inspect at the later of the times specified in paragraphs 
(i)(3)(i) and (i)(3)(ii) of this AD.
    (i) At the time specified in paragraph (i)(1) or (i)(2) of this 
AD, as applicable.
    (ii) Within 10,000 flight cycles after the replacement of the 
part with a new part.

(j) Inspection Compliance Times for Model 747-400 LCF Airplanes

    For Model 747-400 LCF airplanes: Perform inspections to detect 
cracks of all structure identified in Boeing Document No. D6-35022, 
``Supplemental Structural Inspection Document for Model 747 
Airplanes,'' Revision H, dated September 2013; and Boeing Document 
No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection 
Document--Appendix A,'' dated November 2015; at the times specified 
in paragraph (j)(1) or (j)(2) of this AD, as applicable. Once the 
initial inspection has been performed, in order to remain in 
compliance with the maintenance or inspection program, as required 
by paragraph (h) of this AD, repetitive inspections are required at 
the intervals specified in Boeing Document No. D6-35022, 
``Supplemental Structural Inspection Document for Model 747 
Airplanes,'' Revision H, dated September 2013; and Boeing Document 
No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection 
Document--Appendix A,'' dated November 2015. Where SSIs are listed 
in both Boeing Document No. D6-35022, ``Supplemental Structural 
Inspection Document for Model 747 Airplanes,'' Revision H, dated 
September 2013; and Boeing Document No. D6-35022-1, ``747-400 LCF 
Supplemental Structural Inspection Document--Appendix A,'' dated 
November 2015; the SSIs listed in Boeing Document No. D6-35022-1, 
``747-400 LCF Supplemental Structural Inspection Document--Appendix 
A,'' dated November 2015, take precedence. Doing an inspection 
required by this paragraph terminates the corresponding inspection 
required by paragraph (i) of AD 2004-07-22 R1.
    (1) For wing structure: Inspect at the times specified in 
paragraph (j)(1)(i) or (j)(1)(ii) of this AD, whichever occurs 
later.
    (i) Prior to the accumulation of 20,000 total flight cycles or 
115,000 total flight hours, whichever occurs first.
    (ii) Within 1,000 flight cycles or 12 months after the effective 
date of this AD, whichever occurs later.
    (2) For all structure other than wing structure: At the time 
specified in paragraph (j)(2)(i) or (i)(2)(ii) of this AD, whichever 
occurs later.
    (i) At the earlier of the times specified in paragraphs 
(j)(2)(i)(A) and (j)(2)(i)(B) of this AD.
    (A) Prior to the accumulation of 20,000 total flight cycles.
    (B) Within the applicable initial compliance time specified in 
Boeing Document No. D6-35022, ``Supplemental Structural Inspection 
Document for Model 747 Airplanes,'' Revision H, dated September 
2013; and Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental 
Structural Inspection Document--Appendix A,'' dated November 2015. 
Where SSIs are listed in both Boeing Document No. D6-35022, 
``Supplemental Structural Inspection Document for Model 747 
Airplanes,'' Revision H, dated September 2013; and Boeing Document 
No. D6-35022-1, ``747-400 LCF Supplemental Structural Inspection 
Document--Appendix A,'' dated November 2015; the SSIs listed in 
Boeing Document No. D6-35022-1, ``747-400 LCF Supplemental 
Structural Inspection Document--Appendix A,'' dated November 2015, 
take precedence.
    (ii) Within 1,000 flight cycles or 12 months after the effective 
date of this AD, whichever occurs later.

(k) Repair

    If any cracked structure is found during any inspection required 
by paragraph (i) or (j) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (m) of this AD.

(l) Inspection Program for Transferred Airplanes

    Before any airplane that is subject to this AD and that has 
exceeded the applicable compliance times specified in paragraph (i) 
or (j) of this AD can be added to an air carrier's operations 
specifications, a program for the accomplishment of the inspections 
required by this AD must be established in accordance with paragraph 
(l)(1) or (l)(2) of this AD, as applicable.
    (1) For airplanes that have been inspected as specified in this 
AD, the inspection of each SSI must be accomplished by the new 
operator using the previous operator's schedule and inspection 
method, or the new operator's schedule and inspection method, at 
whichever time would result in the earlier accomplishment for that 
SSI inspection. The compliance time for accomplishment of this 
inspection must be measured from the last inspection accomplished by 
the previous operator. After each inspection has been performed 
once, each subsequent inspection must be performed using the new 
operator's schedule and inspection method.
    (2) For airplanes that have not been inspected as specified in 
this AD, the inspection of each SSI required by this AD must be 
accomplished either prior to adding the airplane to the air 
carrier's operations specification, or using a schedule and an 
inspection method approved by the Manager, Seattle Aircraft 
Certification Office (ACO). After each inspection has been performed 
once, each subsequent inspection must be performed using the new 
operator's schedule and inspection method.

(m) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
ACO, send it to the attention of the person identified in paragraph 
(n)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-
AMOC-Requests@faa.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO, to make those findings. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOCs approved for AD 2004-07-22 R1 are approved as AMOCs 
for the corresponding provisions of paragraphs (h), (i), and (j) of 
this AD for the SSIs identified in the AMOC, except for any SSI that 
has an expanded inspection area identified in Boeing Document No. 
D6-35022, ``Supplemental Structural Inspection Document for Model 
747 Airplanes,'' Revision H, dated September 2013; or Boeing 
Document No. D6-35022-1, ``747-400 LCF Supplemental Structural 
Inspection Document--Appendix A,'' dated November 2015.

(n) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; 
fax: 425-917-6590; email: nathan.p.weigand@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.


[[Page 62035]]


    Issued in Renton, Washington, on August 24, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-21147 Filed 9-7-16; 8:45 am]
 BILLING CODE 4910-13-P